阅读说明：本技术 用于制造含有陶瓷基质的复合部件的方法 (Method for producing a composite component comprising a ceramic matrix ) 是由 阿诺·德勒胡兹 埃里克·布伊隆 雅恩·勒佩蒂科尔 于 2018-12-20 设计创作，主要内容包括：本发明涉及一种用于制造复合材料部件的方法,所述复合材料部件包括由陶瓷基质致密的颗粒增强体,所述方法包括以下步骤：通过将包含粘合剂、用于形成所述部件的颗粒增强物的第一陶瓷或碳颗粒以及不同于所述第一颗粒的第二陶瓷或碳颗粒的混合物成形来形成要制造的部件的毛坯；去除或热解所述毛坯中存在的粘合剂以获得所述部件的多孔预制件；以及通过包含金属的熔融组合物渗透所述预制件的孔隙,以获得所述部件。(The invention relates to a method for manufacturing a composite part comprising a particle reinforcement densified by a ceramic matrix, comprising the following steps: forming a blank of a part to be manufactured by shaping a mixture comprising a binder, first ceramic or carbon particles for forming a particulate reinforcement of the part, and second ceramic or carbon particles different from the first particles; removing or pyrolysing the binder present in the blank to obtain a porous preform of the component; and infiltrating the pores of the preform with a molten composition comprising a metal to obtain the part.)

1. A method for manufacturing a composite part comprising a particle reinforcement densified by a ceramic matrix, the method comprising the steps of:

forming a blank of the component to be manufactured by shaping a mixture comprising a binder, first ceramic or carbon particles for forming a particle reinforcement of the component and second ceramic or carbon particles different from the first particles (S4),

removing or pyrolysing the binder present in the blank to obtain a porous preform of the component (S5), and

infiltrating the pores of the preform by a molten composition comprising a metal to obtain the part (S6),

characterized in that, before the infiltration step, the method further comprises a step of hot isostatic pressing the porous preform obtained after removal or pyrolysis of the binder.

2. The method of claim 1, wherein the molten composition comprises silicon.

3. A method according to claim 1 or 2, wherein the first particles are staple fibres.

4. A method according to claim 3, wherein the length of the staple fibres is between 50 and 5000 μm.

5. A method according to claim 4, wherein the length of the staple fibres is between 100 and 300 μm.

6. The method according to claim 1 or 2, wherein the first particles are granules.

7. The method of any one of claims 1 to 6, wherein the median basal volume of the first particles is greater than or equal to the median basal volume of the second particles.

8. The method of any one of claims 1-7, wherein shaping the mixture comprises injecting the mixture into a mold.

9. The method of claim 8, wherein a liquid medium containing the mixture is injected into the mold, the mold may be equipped with a filtering device for the liquid medium, and the step of forming the blank further comprises filtering the liquid medium through the filtering device.

10. The method of any one of claims 1-7, wherein shaping the mixture comprises applying pressure to the mixture.

11. The method of claim 10, wherein shaping the mixture comprises cold isostatic pressing the mixture into a mold.

12. The method of any one of claims 1 to 11, wherein the first particles are silicon carbide.

13. The method of any one of claims 1 to 12, wherein the first particles are coated with an interphase.

14. According to the rightThe method of any one of claims 1 to 13, wherein the second ceramic particles comprise a material selected from the group consisting of: SiC, MoSi₂、TiSi₂、CoSi₂、ZrSi₂、HfSi₂、ZrB₂、HfB₂、TiB₂And mixtures thereof.

15. The method of any one of claims 1 to 14, wherein the volume content of the first particles in the component is between 10% and 70%.

16. The method of any one of claims 1 to 15, wherein the volume content of the second particles in the component is between 30% and 90%.

17. The method of any of claims 1-16, wherein the component is a component for an aircraft turbine.

Background

The present invention relates to the general field of methods for manufacturing components made of ceramic matrix composite materials.

Ceramic Matrix Composites (CMCs) are known for their good mechanical properties, making them suitable for use as structural elements and maintaining these properties at high temperatures, a viable alternative to traditional metal components. Compared with similar metal products, the quality of the products is reduced, so that the products become ideal choices for improving efficiency and reducing pollution and emission of engines in the field of aviation.

CMC components may include a generally continuous fiber reinforcement in the form of a woven fabric that is densified by a ceramic matrix. Thus, the fiber reinforcement comprises generally continuous long fibers, the orientation of which can be adapted to the prevailing stress direction of the component during use. The preform from which the fiber reinforcement is formed must be woven from continuous fibers to the dimensions of the component using a suitable loom (e.g., by two-dimensional or three-dimensional weaving). The weaving step is a lengthy and expensive process that is not the optimal method of making small parts.

Therefore, there is a need for a ceramic matrix composite component manufacturing method that is easy to implement and less costly to manufacture for small components.

Disclosure of Invention

The main object of the present invention is therefore to remedy these drawbacks by proposing a method for manufacturing a composite part comprising a particle reinforcement densified by a ceramic matrix, comprising the following steps:

forming a blank of the component to be manufactured by shaping a mixture comprising a binder, first ceramic or carbon particles for forming the particle reinforcement of the component and second ceramic or carbon particles different from the first particles,

removing or pyrolysing the binder present in the blank to obtain a porous preform of the component, and

infiltrating the pores of the preform with a molten composition comprising a metal to obtain the part.

The method according to the invention thus makes it possible to produce CMC components by a melt infiltration process without the need for weaving fiber reinforcements. The method according to the invention makes it possible to dispense with the step of weaving the fiber reinforcement, due to the step of shaping the mixture filled with the first particles and the second particles and then obtaining the porous preform by removing or pyrolysing the binder. This is particularly advantageous for manufacturing small parts that are not affected by high thermo-mechanical stresses, which means that manufacturing time and costs can be saved. Parts of complex shape and desired dimensions can also be obtained from the method of the invention without additional machining.

The mixture between the binder and the particles may be homogeneous and intimate.

In an exemplary embodiment, the molten composition may include an intermetallic compound. In one exemplary embodiment, the molten composition may include silicon.

The molten composition may consist of pure molten silicon or, alternatively, in the form of a molten alloy of silicon with one or more other ingredients. The molten composition may comprise mainly silicon, i.e. have a silicon content above 50% by mass. The molten composition may, for example, have a silicon content greater than or equal to 75% by mass. The components present in the silicon alloy may be selected from B, Al, Mo, Ti and mixtures thereof. In particular, the molten composition may include molybdenum disilicide (MoSi 2). During infiltration, chemical reactions may occur between the molten composition and carbon (e.g., pyrolysis residue) present in the porous preform, thereby forming silicon carbide (reactive melt infiltration process).

In one exemplary embodiment, the mixture may be heated to fluidize the binder and facilitate the forming step to form the blank. The mixture may also be subjected to a vacuum prior to shaping to remove any air bubbles present in the mixture. The size of the blank may be greater than or equal to the size of the final part so as to leave a porous network inside the blank after removal or pyrolysis of the adhesive. The binder removal or pyrolysis step (also called "debinding") may preferably be carried out under an inert gas, such as argon, to avoid oxidation of the blank, which would reduce its mechanical strength between the different processing steps of the final part. In the following, when referring to an "adhesive removal" step, it is always understood to mean an "adhesive removal or pyrolysis" step, wherein pyrolysis involves removing the adhesive and leaving a residue.

In an exemplary embodiment, the first particles may be short fibers. In other words, the first particles may have a substantially cylindrical shape.

In one exemplary embodiment, the length of the short fiber may preferably be between 50 μm and 5000 μm, or more preferably, the length of the short fiber may be between 100 μm and 300 μm.

In an exemplary embodiment, the short fibers may be obtained from long fibers by mechanical cutting or grinding.

In an exemplary embodiment, the first particles may be fine particles. In other words, the first particles may be spherical or ellipsoidal. In this case, the average size (D50) of the first particles may be between 10 μm and 300 μm, more preferably between 40 μm and 100 μm.

In one exemplary embodiment, the median basal volume of the first particles may be greater than or equal to the median basal volume of the second particles. The fundamental volume of a particle is the volume occupied by that particle.

In an exemplary embodiment, the shaping of the mixture may include injecting the mixture into a mold.

In one exemplary embodiment, the adhesive may comprise at least one thermoplastic polymer. For example, the binder may comprise at least one compound selected from the group consisting of: polyvinyl alcohol (PVA), polyethylene glycol (PEG), polypropylene (PP), Polyoxymethylene (POM), polyethylene terephthalate (PET).

In one exemplary embodiment, the adhesive may comprise at least one thermoset polymer. For example, the binder may comprise at least one compound selected from the group consisting of: epoxy resin, phenolic resin and ceramic precursor resin.

In one exemplary embodiment, the mixture may include two heat-removable adhesives, each having a different removal temperature. Thus, the adhesive removal step may comprise two sub-steps of thermally removing each adhesive at two different temperatures.

In one exemplary embodiment, the mixture may include a first binder removable by dissolution and a second binder removable by heating. Thus, the adhesive removal step may comprise two removal sub-steps: the first adhesive is removed by dissolution and then the second adhesive is removed by heat. This arrangement is advantageous because it allows for more efficient removal of the second adhesive by opening the pores in the blank after dissolution removal of the first adhesive.

In an exemplary embodiment, the liquid medium comprising the mixture may be injected into a mold, the mold may be equipped with a filtration device for the liquid medium, and the step of forming the blank may additionally comprise filtering the liquid medium through the filtration device. The liquid medium may be an aqueous medium or may comprise, for example, an alcohol.

In an exemplary embodiment, the shaping of the mixture may include applying pressure to the mixture. In this case, the binder includes a plasticizer to improve the compactness of the mixture. Such a plasticizer may be stearic acid. In this case, the shaping of the mixture may involve cold isostatic pressing the mixture into a mold.

In an exemplary embodiment, the method may include, prior to the infiltrating step, subjecting the porous preform obtained after removing or pyrolyzing the binder to isostatic pressing. The isostatic pressing step may be performed hot or cold. The isostatic pressing step makes it possible to partially close the porosity resulting from the binder removal or pyrolysis step, in order to control this porosity and facilitate the subsequent infiltration step.

The debinded blank may also be subjected to a free (i.e., stress free) sintering heat treatment again prior to the infiltration step to control the porosity of the debinded blank. The free sintering heat treatment may be performed after the cold isostatic pressing step and before the hot isostatic pressing step.

In an exemplary embodiment, the first particles may be made of silicon carbide. In the case of staple fibers, their oxygen content may be less than or equal to 1 atomic percent. Such staple fibers may be, for example, Hi-Nicalon S-type fibers sold by the company NGS, Japan. Alternatively, the staple fibers may be made of a material selected from the group consisting of: carbon, oxides, e.g. alumina (Al)₂O₃)。

In one exemplary embodiment, the first particles may be coated with a mesophase. Such mesophases may be made, for example, of pyrolytic carbon (PyC), Boron Nitride (BN) or silicon carbide (SiC). The mesophase may comprise several layers, each layer comprising a different material. The mesophase has the function of reducing the brittleness of the composite material, promoting the deflection of possible cracks that reach the mesophase after propagation in the matrix, thus preventing or delaying the breaking of the reinforcement caused by such cracks. The mesophase also protects the first particles of the fibers of the matrix material during their formation.

The mesophase may be deposited on the first particles before the first particles are introduced into the mixture. If short fibers, the mesophase may be deposited on the long fibers before they are cut or ground. The mesophase may be deposited directly on the short fibers by a Chemical Vapor Deposition (CVD) process or by an electrolytic deposition process or by molten salts. It is also possible to deposit a ceramic coating compatible with the matrix material to be formed instead of or on the mesophase.

In one exemplary embodiment, the second ceramic particles may be made of a material selected from the group consisting of: SiC, MoSi₂、TiSi₂、CoSi₂、ZrSi₂、HfSi₂、ZrB₂、HfB₂、TiB₂And mixtures thereof.

In an exemplary embodiment, the volume content of the first particles in the component may be between 10% and 70%, preferably between 25% and 50%.

In an exemplary embodiment, the volume content of the second particles in the component may be between 30% and 90%, preferably between 50% and 75%.

In an exemplary embodiment, the average size (D50) of the second particles may be between 0.5 μm and 200 μm, more preferably between 0.7 μm and 75 μm.

Drawings

Further features and advantages of the invention will become apparent from the description given below, with reference to the accompanying drawings, which illustrate exemplary embodiments without any limiting character. FIG. 1 is a flow chart illustrating various steps of a method according to an embodiment of the invention.

Detailed Description

The steps of the method according to an embodiment of the invention will now be described in connection with the flow chart in fig. 1. The object here is to obtain a ceramic matrix composite component. Such a component may be an aerospace component, such as a component for an aerospace turbine. Such a component may be, for example, a vanelet.

In step S1, first ceramic or carbon particles may be obtained that will be used to form a particle (e.g., fiber) reinforcement of the component to be fabricated. When the first particles are short fibers, they may be obtained by grinding or mechanically cutting long fibers in a manner known per se. The median length of the staple fibers may be between 50 μm and 5000 μm or between 100 μm and 300 μm. The size distribution of the first particles need not be monodisperse but may be polydisperse.

The first particles may optionally be coated with a mesophase coating (step S2). For short fibers, the coating can be done directly or by coating long fibers before cutting or grinding. The thickness of the mesophase may be, for example, between 10nm and 1000nm, and, for example, between 10nm and 500 nm. The mesophase may be a single layer or multiple layers. The intermediate phase may comprise at least one layer of pyrolytic carbon (PyC), Boron Nitride (BN), silicon-doped boron nitride (BN (si), with a silicon mass fraction of between 5% and 40%, the remainder being boron nitride) or boron-doped carbon (BC, with a boron atomic fraction of between 5% and 20%, the remainder being carbon). The deposition of the mesophase can be carried out directly on the short fibers by a CVD process or an electroplating process or by a molten salt. The mesophase has here the defibrination function of the composite material, which promotes the deflection of possible cracks that reach the mesophase after propagation in the matrix, thereby preventing or delaying the breaking of the reinforcement caused by such cracks. The mesophase may also protect the reinforcement during subsequent steps of matrix formation. It is also possible to deposit a ceramic coating compatible with the matrix material to be formed (for example by CVI) instead of or on top of the mesophase, for example by CVI.

In step S3, a mixture including a binder, first ceramic or carbon particles, and second ceramic particles may then be prepared to form a matrix of the component. The binder may for example comprise a polymer, such as a thermoplastic or thermosetting resin or a plasticizer. The mixture may include several binders. It may be advantageous to heat the mixture to fluidize the binder to facilitate mixing and allow for better homogenization. The mixing temperature is then dependent on the organic binder used to avoid thermal degradation and premature polymerization. The mixture may also be prepared under vacuum to reduce the presence of air bubbles in the mixture. The mixture thus prepared can, for example, be granulated for later use or injected directly in the next step.

In step S4, a blank of the part is formed by shaping the mixture prepared in step S3. Several ways of performing this step will be described below.

According to a first alternative, the forming step can be carried out by injecting the mixture into the mould cavity. The mold cavity for injection may have larger dimensions than the final part because a porous network is required to effectively perform the infiltration step (step S6). The mould may comprise a nozzle, the size of which is adapted in a known manner to the size of the first and second particles, and to the binder and the selected injection pressure and temperature. If necessary, the mold may be temperature controlled to control possible curing of the adhesive after injection. This control may also be used to avoid preferential orientation of the first particles when they correspond to short fibers near the die wall. The injection may be performed using a mixture preheated to a temperature that allows the adhesive to flow. The injection may be performed at a pressure between 50 bar and 3000 bar. Once the mixture is injected into the mold and the blank is molded, the blank may be demolded. The resulting blank is in an "embryonic" or plastic state. As noted above, the blank may generally be larger than the final part.

In a second alternative, the mold may be equipped with a filtering device, and the liquid medium comprising a mixture of first particles and second particles dispersed in the liquid medium is injected into the mold, and the step S4 of forming the blank further comprises filtering the liquid medium through the filtering device. The liquid medium may be an aqueous medium or contain an alcohol. The liquid medium may preferably comprise polyvinyl alcohol (PVA). It may be a slurry. During the injection/filtration process, the first granules and the second granules are retained inside the mold by the filtration device and gradually formed into a blank.

In a third alternative, the binder may include a plasticizer, and the binder shaping step includes applying pressure to the mixture, such as cold isostatic pressing of the mixture. The plasticizer to facilitate compaction may be stearic acid. The mixture may then be placed directly into a mold, and pressure may be applied to the mixture through the mold to shape the mixture.

In step S5, the adhesive in the blank is removed or pyrolyzed to produce a debonded blank. The conditions of the adhesive removal or pyrolysis step S5 generally depend on the nature of the adhesive removed in a manner known per se. In particular, some adhesives may be thermally removed, i.e. the temperature causes them to decompose and/or evaporate, while others may be chemically removed, for example by dissolving in a suitable solvent. Step S5 may involve pyrolysis, in which case pyrolysis residue may remain in the debonded blank. Step S5 may be performed in a neutral atmosphere (e.g., argon) to retain the carbon skeleton in the boule until the end of the removal step, thereby ensuring better retention of the boule and also reducing the risk of oxidation of the boule.

It is advantageous to use several adhesives, for example two adhesives which can be removed in two separate removal steps. In one example, the first adhesive is first removed by dissolving, and then the second adhesive is thermally removed. In another example, the first adhesive may be thermally removed at a first removal temperature, and the second adhesive may be thermally removed at a second removal temperature that is higher than the first removal temperature. The continuous removal of both binders reduces the risk of the preform breaking in step S5 by opening the pores in the preform after the removal of the first binder, through which pores the second binder can be lifted out of the preform. The dimensions of the preform generally do not change after debindering step S5. Thus, the debinded blank or porous preform comprises the first particle and the second particle and has non-zero porosity previously occupied by the binder.

Then, in step S6, the pores of the preform are infiltrated with a molten composition comprising a metal (e.g., an intermetallic compound or silicon) to obtain the part. This infiltration step corresponds to a melt infiltration step (MI or RMI process). The molten composition or infiltration composition may consist of pure molten silicon, or alternatively, be in the form of a molten alloy of silicon with one or more other ingredients. After step S6, a CMC part is obtained.

After step S5 of removing or pyrolysing the binder present in the blank, and before the infiltration step S6, the porous preform is subjected to a step of hot isostatic pressing, in order to close part of the pores if the porosity is too high, before step S6. The hot isostatic pressing step is preferably carried out under a jacket to ensure uniform compaction of the porous preform. The pressure applied is preferably between 1000 and 2000 bar. The jacket may comprise graphite and boron nitride. This step can reduce the porosity of the debonded ingot (typically between 30% and 40%) to, for example, about 10% porosity in order to maintain a sufficient network of interconnected pores and have a certain porosity to ensure better capillary rise of the molten metal in the preform. In addition, this hot isostatic pressing step performed before infiltration makes it possible to reduce the volume of liquid metal that can react with the reinforcement during infiltration, thereby protecting the reinforcement by reducing the risk of dissolution of the reinforcement by the liquid metal. The hot isostatic pressing step may be performed at a temperature between 1000 ℃ and 1600 ℃, depending on the matrix material involved. For a titanium disilicide matrix, the temperature may be between 1100 ℃ and 1500 ℃, for example.